The results of development and manufacture of a micro gas turbine engine for an unmanned aerial vehicle are presented. The calculation features of the main elements of the engine blading section, namely, a centrifugal compressor, a reverse-flow combustor, and a radial-axial turbine are considered. The design of the inlet and output duct, rotor bearings, and lubrication system is described.


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    Title :

    Micro Gas Turbine Engine for Unmanned Aerial Vehicles


    Additional title:

    Russ. Aeronaut.


    Contributors:

    Published in:

    Russian Aeronautics ; 62 , 4 ; 651-660


    Publication date :

    2019-10-01


    Size :

    10 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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